Flight altitude estimation systems and methods

ABSTRACT

Unmanned aircraft systems (UASs) and related techniques are provided to improve the operation of unmanned mobile sensor or survey platforms. A flight altitude estimation system includes a logic device configured to communicate with a communication module and a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the communication module is configured to establish a communication link with a base station associated with the mobile platform, and the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area. The logic device is configured to receive demark pressure data from a demark barometer coupled to the base station and determine a differential flight altitude estimation based, at least in part, on received flight pressure data and demark pressure data, a reference flight pressure and a reference demark pressure corresponding to a flight initiation location of the base station.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of and priority to U.S. Provisional Patent Application No. 62/963,128 filed Jan. 19, 2020 and entitled “FLIGHT ALTITUDE ESTIMATION SYSTEMS AND METHODS,” which is incorporated herein by reference in its entirety.

This application is related to International Patent Application No. PCT/US2019/025458 filed Apr. 2, 2019 and entitled “RADIO LINK COVERAGE MAP AND LOSS MITIGATION SYSTEMS AND METHODS,” which is hereby incorporated by reference in its entirety. PCT/US2019/025458 claims the benefit of U.S. Provisional Patent Application No. 62/664,719 filed Apr. 30, 2018 and entitled “RADIO LINK COVERAGE MAP AND LOSS MITIGATION SYSTEMS AND METHODS” which is hereby incorporated by reference in its entirety.

This application is related to U.S. patent application Ser. No. 16/088,040 filed Sep. 24, 2018 and entitled “PERSISTENT AERIAL RECONNAISSANCE AND COMMUNICATION SYSTEM,” which is hereby incorporated by reference in its entirety. U.S. patent application Ser. No. 16/088,040 is a 35 U.S.C. 371 national stage filing of PCT Patent Application No. PCT/US2017/024152 filed Mar. 24, 2017 and entitled “PERSISTENT AERIAL RECONNAISSANCE AND COMMUNICATION SYSTEM,” which is hereby incorporated by reference in its entirety. PCT/US2017/024152 claims the benefit of U.S. Provisional patent Application No. 62/312,887 filed Mar. 24, 2016, U.S. Provisional Patent Application No. 62/315,873 filed Mar. 31, 2016, U.S. Provisional Patent Application No. 62/321,292 filed on Apr. 12, 2016, U.S. Provisional Patent Application No. 62/420,548 filed on Nov. 10, 2016, U.S. Provisional patent Application No. 62/463,536 filed on Feb. 24, 2017, all of which are hereby incorporated by reference in their entirety.

TECHNICAL FIELD

The present invention relates generally to unmanned sensor platforms and, more particularly, to systems and methods for flight altitude estimation of unmanned aerial vehicles.

BACKGROUND

Modern unmanned sensor platforms, such as unmanned aerial vehicles (UAVs), remotely operated underwater vehicles (ROVs), unmanned (water) surface vehicles (USVs), and unmanned ground vehicles (UGVs) are able to operate over long distances and in all environments; rural, urban, and even underwater. Operation of such platforms typically includes real-time data transmissions between the unmanned sensor platform and a base station, which often includes a display to efficiently convey telemetry, imagery, and other sensor data captured by the platform to an operator. The operator, or a system incorporating such platforms, is often required to pilot or otherwise control or monitor an unmanned sensor platform throughout an entire mission relying solely on received data from the unmanned sensor platform. As such, non-automated or unreliably automated aspects related to safe and precise control of the unmanned sensor platform can significantly reduce the operational flexibility of the platform and/or its constituent system.

Thus, there is a need in the art for methodologies to automate or more-reliably automate control of unmanned sensor platforms and increase the operational flexibility of such systems.

SUMMARY

Flight altitude estimation systems and related techniques are provided to improve the operation of unmanned aerial vehicles (UAVs) and/or unmanned aircraft systems (UASs) incorporating one or more such UAVs. One or more embodiments of the described flight altitude estimation systems may advantageously include a communication module to establish one or more wired and/or wireless communication links between a ground station and a UAV of the UAS, a flight barometer to measure and provide an atmospheric pressure corresponding to an estimated absolute altitude of the mobile platform, a controller to control operation of the communication module, the flight barometer, and/or the mobile platform, and one or more additional sensors to measure and provide sensor data corresponding to maneuvering and/or other operation of the mobile platform. In various embodiments, such additional sensors may include a remote sensor system configured to capture sensor data of a survey area from which a two and/or three dimensional spatial map of the survey area may be generated. For example, the mapping system may include one or more visible spectrum and/or infrared cameras and/or other remote sensor systems coupled to the UAV.

In one embodiment, a system includes a logic device configured to communicate with a communication module and a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the communication module is configured to establish a communication link with a base station associated with the mobile platform, the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area. The logic device may be configured to receive flight pressure data from the flight barometer corresponding to one or more positions of the mobile platform within the survey area; receive demark pressure data from a demark barometer coupled to the base station; and determine a differential flight altitude estimation based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station.

In another embodiment, a method includes receiving flight pressure data from a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area and the flight pressure data corresponds to one or more positions of the mobile platform within the survey area; receiving demark pressure data from a demark barometer coupled to the base station; and determining a differential flight altitude estimation based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station.

The scope of the invention is defined by the claims, which are incorporated into this section by reference. A more complete understanding of embodiments of the present invention will be afforded to those skilled in the art, as well as a realization of additional advantages thereof, by a consideration of the following detailed description of one or more embodiments. Reference will be made to the appended sheets of drawings that will first be described briefly.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates a diagram of an unmanned aircraft system (UAS) in accordance with an embodiment of the disclosure.

FIG. 2 illustrates a diagram of mobile platforms (UAVs) of a UAS in accordance with an embodiment of the disclosure.

FIG. 3A illustrates a diagram of a UAS including a tethered UAV in accordance with an embodiment of the disclosure.

FIG. 3B illustrates a diagram of communication and power interconnections for a UAS including a tethered UAV in accordance with an embodiment of the disclosure.

FIG. 4 illustrates a flow diagram of a control loop to determine a flight altitude estimate in accordance with an embodiment of the disclosure.

FIGS. 5A-B illustrate graphs of atmospheric pressure trends.

FIG. 6 illustrates a flow diagram of a control loop to determine a flight altitude estimate in accordance with an embodiment of the disclosure.

FIG. 7 illustrates a flow diagram of various operations to provide flight altitude estimations for a UAS in accordance with an embodiment of the disclosure.

Embodiments of the present invention and their advantages are best understood by referring to the detailed description that follows. It should be appreciated that like reference numerals are used to identify like elements illustrated in one or more of the figures.

DETAILED DESCRIPTION

Flight altitude estimation systems and related techniques are provided to improve the operational flexibility and reliability of unmanned aircraft systems (UASs) including unmanned sensor platforms, such as unmanned aerial vehicles (UAVs). A flight altitude estimation system may advantageously include a communication module to establish one or more wired and/or wireless communication links between a ground station and a UAV of the UAS, a flight barometer to measure and provide an atmospheric pressure corresponding to an estimated absolute altitude of the mobile platform, a controller to control operation of the communication module, the flight barometer, and/or the mobile platform, and one or more additional sensors to measure and provide sensor data corresponding to maneuvering and/or other operation of the mobile platform. In various embodiments, such additional sensors may include a remote sensor system configured to capture sensor data of a survey area from which a two and/or three dimensional spatial map of the survey area may be generated. For example, the mapping system may include one or more visible spectrum and/or infrared cameras and/or other remote sensor systems coupled to the UAV.

Atmospheric pressure is a known source for estimating the altitude for a UAV. The conventional technique to estimate the above-ground height of a UAV involves using the difference between a live atmospheric pressure reading from a flight pressure sensor mounted the UAV and a non-live reference pressure that is the recorded pressure when the UAV left the ground. However, ambient atmospheric pressure is always changing due to temperature rise/drop, weather system movement, etc. Such changes are typically a relatively slow process compared to the time span of typical untethered UAV flights, so the assumption of a constant reference pressure is reasonable for flights lasting less than one hour, for example. By contrast, for tethered flight, which can be prolonged with continuous supply of power, the change of ambient pressure renders the recorded pressure at the ground relatively unreliable. For example, a 200 Pa pressure change, which can occur in a few hours even on a relatively calm day, equates to about a 20 meter height estimate drift.

Other sources for estimating height exist, but they are relatively unreliable and only mitigate the height drift issue rather than eliminate it. For example, an ultrasound/laser/lidar sensor or even computer vision usually has limited detecting range, typically less than 10 meters. Such detection is helpful when a UAV is close to the ground, but not when the UAV is tasked with hovering at a fixed altitude, or according to designated surveillance routes, high up in the air. Also, such sensors always provide relative measurements, which means they follow the elevation change of terrain, so if a UAV flies over a cliff or exits or enters a forest of trees, the altitude estimate can jump up/down dramatically and result in unstable flight control. Altitude estimates from GNSSs (Global Navigation Satellite Systems), such as GPS, GLONASS, Galileo, and Beidou, are not sufficiently accurate for reliable autonomous or assisted flight. For example, GPS altitude error can easily exceed 10 meters.

Atmospheric pressure can provide a reliable way to estimating flight altitude, but the reference pressure on the ground must be updated to compensate for drift. As such, embodiments described herein include a demark pressure sensor mounted to a ground control station or base station, which can provide live or substantially real time ambient reference pressures to a UAS. With such information, a relatively reliable flight altitude estimate may be determined based on the differential atmospheric pressure between a UAV and its associated base station, as described herein.

FIG. 1 illustrates a block diagram of UAS 100 in accordance with an embodiment of the disclosure. In some embodiments, system 100 may be configured to fly over a scene, through a structure, or approach a target and image or sense the scene, structure, or target, or portions thereof, using gimbal system 122 to aim imaging system/sensor payload 140 at the scene, structure, or target, or portions thereof. Resulting imagery and/or other sensor data may be processed (e.g., by sensor payload 140, platform 110, and/or base station 130) and displayed to a user through use of user interface 132 (e.g., one or more displays such as a multi-function display (MFD), a portable electronic device such as a tablet, laptop, or smart phone, or other appropriate interface) and/or stored in memory for later viewing and/or analysis. In some embodiments, system 100 may be configured to use such imagery and/or sensor data to control operation of platform 110 and/or sensor payload 140, as described herein, such as controlling gimbal system 122 to aim sensor payload 140 towards a particular direction or controlling propulsion system 124 to move platform 110 to a desired position in a scene or structure or relative to a target.

In the embodiment shown in FIG. 1, UAS 100 includes platform 110, optional base station 130, and at least one imaging system/sensor payload 140. Platform 110 may be a mobile platform configured to move or fly and position and/or aim sensor payload 140 (e.g., relative to a designated or detected target). As shown in FIG. 1, platform 110 may include one or more of a controller 112, an orientation sensor 114, a gyroscope/accelerometer 116, a global navigation satellite system (GNSS) 118, a communications module 120, a gimbal system 122, a propulsion system 124, and other modules 126. Operation of platform 110 may be substantially autonomous and/or partially or completely controlled by optional base station 130, which may include one or more of a user interface 132, a communications module 134, and other modules 136. In other embodiments, platform 110 may include one or more of the elements of base station 130, such as with various types of manned aircraft, terrestrial vehicles, and/or surface or subsurface watercraft. Sensor payload 140 may be physically coupled to platform 110 and be configured to capture sensor data (e.g., visible spectrum images, infrared images, narrow aperture radar data, and/or other sensor data) of a target position, area, and/or object(s) as selected and/or framed by operation of platform 110 and/or base station 130. In some embodiments, one or more of the elements of system 100 may be implemented in a combined housing or structure that can be coupled to or within platform 110 and/or held or carried by a user of system 100.

Controller 112 may be implemented as any appropriate logic device (e.g., processing device, microcontroller, processor, application specific integrated circuit (ASIC), field programmable gate array (FPGA), memory storage device, memory reader, or other device or combinations of devices) that may be adapted to execute, store, and/or receive appropriate instructions, such as software instructions implementing a control loop for controlling various operations of platform 110 and/or other elements of system 100, for example. Such software instructions may also implement methods for processing infrared images and/or other sensor signals, determining sensor information, providing user feedback (e.g., through user interface 132), querying devices for operational parameters, selecting operational parameters for devices, or performing any of the various operations described herein (e.g., operations performed by logic devices of various devices of system 100).

In addition, a non-transitory medium may be provided for storing machine readable instructions for loading into and execution by controller 112. In these and other embodiments, controller 112 may be implemented with other components where appropriate, such as volatile memory, non-volatile memory, one or more interfaces, and/or various analog and/or digital components for interfacing with devices of system 100. For example, controller 112 may be adapted to store sensor signals, sensor information, parameters for coordinate frame transformations, calibration parameters, sets of calibration points, and/or other operational parameters, over time, for example, and provide such stored data to a user using user interface 132. In some embodiments, controller 112 may be integrated with one or more other elements of platform 110, for example, or distributed as multiple logic devices within platform 110, base station 130, and/or sensor payload 140.

In some embodiments, controller 112 may be configured to substantially continuously monitor and/or store the status of and/or sensor data provided by one or more elements of platform 110, sensor payload 140, and/or base station 130, such as the position and/or orientation of platform 110, sensor payload 140, and/or base station 130, for example, and the status of a communication link established between platform 110, sensor payload 140, and/or base station 130 (e.g., including packet loss of transmitted and received data between elements of system 100, such as with digital communication links). In particular, packet loss is traditionally estimated as a percentage of packets lost vs packets sent to a designated target. However, controller 112 may also be configured to categorize packet loss, such as a simplified scaling methodology that may be used to categorize the amount of packet loss acceptable for a specific use of platform 110 and/or sensor payload 140. Regardless, such communication links may be configured to be established and then transmit data between elements of system 100 substantially continuously throughout operation of system 100, where such data includes various types of sensor data, control parameters, and/or other data.

Orientation sensor 114 may be implemented as one or more of a compass, float, accelerometer, and/or other device capable of measuring an orientation of platform 110 (e.g., magnitude and direction of roll, pitch, and/or yaw, relative to one or more reference orientations such as gravity and/or Magnetic North), gimbal system 122, imaging system/sensor payload 140, and/or other elements of system 100, and providing such measurements as sensor signals and/or data that may be communicated to various devices of system 100. Gyroscope/accelerometer 116 may be implemented as one or more electronic sextants, semiconductor devices, integrated chips, accelerometer sensors, accelerometer sensor systems, or other devices capable of measuring angular velocities/accelerations and/or linear accelerations (e.g., direction and magnitude) of platform 110 and/or other elements of system 100 and providing such measurements as sensor signals and/or data that may be communicated to other devices of system 100 (e.g., user interface 132, controller 112).

GNSS 118 may be implemented according to any global navigation satellite system, including a GPS, GLONASS, and/or Galileo based receiver and/or other device capable of determining absolute and/or relative position of platform 110 (e.g., or an element of platform 110) based on wireless signals received from space-born and/or terrestrial sources (e.g., eLoran, and/or other at least partially terrestrial systems), for example, and capable of providing such measurements as sensor signals and/or data (e.g., coordinates) that may be communicated to various devices of system 100. In some embodiments, GNSS 118 may include an altimeter, for example, or may be used to provide an absolute altitude.

Communications module 120 may be implemented as any wired and/or wireless communications module configured to transmit and receive analog and/or digital signals between elements of system 100. For example, communications module 120 may be configured to receive flight control signals and/or data from base station 130 and provide them to controller 112 and/or propulsion system 124. In other embodiments, communications module 120 may be configured to receive images and/or other sensor information (e.g., visible spectrum and/or infrared still images or video images) from sensor payload 140 and relay the sensor data to controller 112 and/or base station 130. In some embodiments, communications module 120 may be configured to support spread spectrum transmissions, for example, and/or multiple simultaneous communications channels between elements of system 100. Wireless communication links may include one or more analog and/or digital radio communication links, such as WiFi and others, as described herein, and may be direct communication links established between elements of system 100, for example, or may be relayed through one or more wireless relay stations configured to receive and retransmit wireless communications.

In some embodiments, communications module 120 may be configured to monitor the status of a communication link established between platform 110, sensor payload 140, and/or base station 130 (e.g., including packet loss of transmitted and received data between elements of system 100, such as with digital communication links). Such status information may be provided to controller 112, for example, or transmitted to other elements of system 100 for monitoring, storage, or further processing, as described herein. In particular, communications module 120 may be configured to monitor packet loss of communications between platform 110 and base station 130 and/or categorize such packet loss according to an acceptable level of packet loss for a particular use or application associated with operation and/or a status of platform 110 and/or other elements of system 100. Regardless, communication links established by communication module 120 may be configured to transmit data between elements of system 100 substantially continuously throughout operation of system 100, where such data includes various types of sensor data, control parameters, and/or other data, as described herein.

In some embodiments, gimbal system 122 may be implemented as an actuated gimbal mount, for example, that may be controlled by controller 112 to stabilize sensor payload 140 relative to a target or to aim sensor payload 140 according to a desired direction and/or relative position. As such, gimbal system 122 may be configured to provide a relative orientation of sensor payload 140 (e.g., relative to an orientation of platform 110) to controller 112 and/or communications module 120 (e.g., gimbal system 122 may include its own orientation sensor 114). In other embodiments, gimbal system 122 may be implemented as a gravity driven mount (e.g., non-actuated). In various embodiments, gimbal system 122 may be configured to provide power, support wired communications, and/or otherwise facilitate operation of articulated sensor/sensor payload 140. In further embodiments, gimbal system 122 may be configured to couple to a laser pointer, range finder, and/or other device, for example, to support, stabilize, power, and/or aim multiple devices (e.g., sensor payload 140 and one or more other devices) substantially simultaneously.

Propulsion system 124 may be implemented as one or more propellers, turbines, or other thrust-based propulsion systems, and/or other types of propulsion systems that can be used to provide motive force and/or lift to platform 110 and/or to steer platform 110. In some embodiments, propulsion system 124 may include multiple propellers (e.g., a tri, quad, hex, oct, or other type “copter”) that can be controlled (e.g., by controller 112) to provide lift and motion for platform 110 and to provide an orientation for platform 110. In other embodiments, propulsion system 110 may be configured primarily to provide thrust while other structures of platform 110 provide lift, such as in a fixed wing embodiment (e.g., where wings provide the lift) and/or an aerostat embodiment (e.g., balloons, airships, hybrid aerostats). In various embodiments, propulsion system 124 may be implemented with a portable power supply, such as a battery and/or a combustion engine/generator and fuel supply.

Other modules 126 may include other and/or additional sensors, actuators, communications modules/nodes, and/or user interface devices, for instance, and may be used to provide additional environmental information related to operation of platform 110, for example. In some embodiments, other modules 126 may include a humidity sensor, a wind and/or water temperature sensor, a barometer (e.g., a flight barometer), an altimeter, a radar system, a proximity sensor, a visible spectrum camera or infrared camera (with an additional mount), an irradiance detector, and/or other environmental sensors providing measurements and/or other sensor signals that can be displayed to a user and/or used by other devices of system 100 (e.g., controller 112) to provide operational control of platform 110 and/or system 100.

In some embodiments, other modules 126 may include one or more actuated and/or articulated devices (e.g., multi-spectrum active illuminators, visible and/or IR cameras, radars, sonars, and/or other actuated devices) coupled to platform 110, where each actuated device includes one or more actuators adapted to adjust an orientation of the device, relative to platform 110, in response to one or more control signals (e.g., provided by controller 112). In particular, other modules 126 may include a stereo vision system configured to provide image data that may be used to calculate or estimate a position of platform 110, for example, or to calculate or estimate a relative position of a navigational hazard in proximity to platform 110. In various embodiments, controller 130 may be configured to use such proximity and/or position information to help safely pilot platform 110 and/or monitor communication link quality, as described herein. One or more such cameras/vision systems (e.g., other modules 126) may be used as a position sensor and configured to provide a position of platform 110 via visual odometry, simultaneous localization and mapping (SLAM), and/or other techniques, as a supplement and/or alternative to GNSS 118, such as when GNSS signals are effective blocked or jammed by walls, buildings, and/or environmental electromagnetic noise.

User interface 132 of base station 130 may be implemented as one or more of a display, a touch screen, a keyboard, a mouse, a joystick, a knob, a steering wheel, a yoke, and/or any other device capable of accepting user input and/or providing feedback to a user. In various embodiments, user interface 132 may be adapted to provide user input (e.g., as a type of signal and/or sensor information transmitted by communications module 134 of base station 130) to other devices of system 100, such as controller 112. User interface 132 may also be implemented with one or more logic devices (e.g., similar to controller 112) that may be adapted to store and/or execute instructions, such as software instructions, implementing any of the various processes and/or methods described herein. For example, user interface 132 may be adapted to form communication links, transmit and/or receive communications (e.g., infrared images and/or other sensor signals, control signals, sensor information, user input, and/or other information), for example, or to perform various other processes and/or methods described herein.

In one embodiment, user interface 132 may be adapted to display a time series of various sensor information and/or other parameters as part of or overlaid on a graph or map, which may be referenced to a position and/or orientation of platform 110 and/or other elements of system 100. For example, user interface 132 may be adapted to display a time series of positions, headings, and/or orientations of platform 110 and/or other elements of system 100 overlaid on a geographical map, which may include one or more graphs indicating a corresponding time series of actuator control signals, sensor information, and/or other sensor and/or control signals.

In some embodiments, user interface 132 may be adapted to accept user input including a user-defined target heading, waypoint, route, and/or orientation for an element of system 100, for example, and to generate control signals to cause platform 110 to move according to the target heading, route, and/or orientation, or to aim sensor payload 140 accordingly. In other embodiments, user interface 132 may be adapted to accept user input modifying a control loop parameter of controller 112, for example.

In further embodiments, user interface 132 may be adapted to accept user input including a user-defined target attitude, orientation, and/or position for an actuated or articulated device (e.g., sensor payload 140) associated with platform 110, for example, and to generate control signals for adjusting an orientation and/or position of the actuated device according to the target attitude, orientation, and/or position. Such control signals may be transmitted to controller 112 (e.g., using communications modules 134 and 120), which may then control platform 110 accordingly.

Communications module 134 may be implemented as any wired and/or wireless communications module configured to transmit and receive analog and/or digital signals between elements of system 100. For example, communications module 134 may be configured to transmit flight control signals from user interface 132 to communications module 120 or 144. In other embodiments, communications module 134 may be configured to receive sensor data (e.g., visible spectrum and/or infrared still images or video images, or other sensor data) from sensor payload 140. In some embodiments, communications module 134 may be configured to support spread spectrum transmissions, for example, and/or multiple simultaneous communications channels between elements of system 100. In various embodiments, communications module 134 may be configured to monitor the status of a communication link established between base station 130, sensor payload 140, and/or platform 110 (e.g., including packet loss of transmitted and received data between elements of system 100, such as with digital communication links), as described herein. Such status information may be provided to user interface 132, for example, or transmitted to other elements of system 100 for monitoring, storage, or further processing, as described herein.

Other modules 136 of base station 130 may include other and/or additional sensors, actuators, communications modules/nodes, and/or user interface devices used to provide additional environmental information associated with base station 130, for example. In some embodiments, other modules 136 may include a humidity sensor, a wind and/or water temperature sensor, a barometer (e.g., a demark barometer), a radar system, a visible spectrum camera, an infrared camera, a GNSS, and/or other environmental sensors providing measurements and/or other sensor signals that can be displayed to a user and/or used by other devices of system 100 (e.g., controller 112) to provide operational control of platform 110 and/or system 100 or to process sensor data to compensate for environmental conditions, such as an water content in the atmosphere approximately at the same altitude and/or within the same area as platform 110 and/or base station 130, for example. In some embodiments, other modules 136 may include one or more actuated and/or articulated devices (e.g., multi-spectrum active illuminators, visible and/or IR cameras, radars, sonars, and/or other actuated devices), where each actuated device includes one or more actuators adapted to adjust an orientation of the device in response to one or more control signals (e.g., provided by user interface 132).

In embodiments where imaging system/sensor payload 140 is implemented as an imaging device, imaging system/sensor payload 140 may include imaging module 142, which may be implemented as a cooled and/or uncooled array of detector elements, such as visible spectrum and/or infrared sensitive detector elements, including quantum well infrared photodetector elements, bolometer or microbolometer based detector elements, type II superlattice based detector elements, and/or other infrared spectrum detector elements that can be arranged in a focal plane array. In various embodiments, imaging module 142 may include one or more logic devices (e.g., similar to controller 112) that can be configured to process imagery captured by detector elements of imaging module 142 before providing the imagery to memory 146 or communications module 144. More generally, imaging module 142 may be configured to perform any of the operations or methods described herein, at least in part, or in combination with controller 112 and/or user interface 132.

In some embodiments, sensor payload 140 may be implemented with a second or additional imaging modules similar to imaging module 142, for example, that may include detector elements configured to detect other electromagnetic spectrums, such as visible light, ultraviolet, and/or other electromagnetic spectrums or subsets of such spectrums. In various embodiments, such additional imaging modules may be calibrated or registered to imaging module 142 such that images captured by each imaging module occupy a known and at least partially overlapping field of view of the other imaging modules, thereby allowing different spectrum images to be geometrically registered to each other (e.g., by scaling and/or positioning). In some embodiments, different spectrum images may be registered to each other using pattern recognition processing in addition or as an alternative to reliance on a known overlapping field of view.

Communications module 144 of sensor payload 140 may be implemented as any wired and/or wireless communications module configured to transmit and receive analog and/or digital signals between elements of system 100. For example, communications module 144 may be configured to transmit infrared images from imaging module 142 to communications module 120 or 134. In other embodiments, communications module 144 may be configured to receive control signals (e.g., control signals directing capture, focus, selective filtering, and/or other operation of sensor payload 140) from controller 112 and/or user interface 132. In some embodiments, communications module 144 may be configured to support spread spectrum transmissions, for example, and/or multiple simultaneous communications channels between elements of system 100. In various embodiments, communications module 144 may be configured to monitor the status of a communication link established between sensor payload 140, base station 130, and/or platform 110 (e.g., including packet loss of transmitted and received data between elements of system 100, such as with digital communication links), as described herein. Such status information may be provided to imaging module 142, for example, or transmitted to other elements of system 100 for monitoring, storage, or further processing, as described herein.

Memory 146 may be implemented as one or more machine readable mediums and/or logic devices configured to store software instructions, sensor signals, control signals, operational parameters, calibration parameters, infrared images, and/or other data facilitating operation of system 100, for example, and provide it to various elements of system 100. Memory 146 may also be implemented, at least in part, as removable memory, such as a secure digital memory card for example including an interface for such memory.

Orientation sensor 148 of sensor payload 140 may be implemented similar to orientation sensor 114 or gyroscope/accelerometer 116, and/or any other device capable of measuring an orientation of sensor payload 140, imaging module 142, and/or other elements of sensor payload 140 (e.g., magnitude and direction of roll, pitch, and/or yaw, relative to one or more reference orientations such as gravity and/or Magnetic North) and providing such measurements as sensor signals that may be communicated to various devices of system 100. Gyroscope/accelerometer (e.g., angular motion sensor) 150 of sensor payload 140 may be implemented as one or more electronic sextants, semiconductor devices, integrated chips, accelerometer sensors, accelerometer sensor systems, or other devices capable of measuring angular velocities/accelerations (e.g., angular motion) and/or linear accelerations (e.g., direction and magnitude) of sensor payload 140 and/or various elements of sensor payload 140 and providing such measurements as sensor signals that may be communicated to various devices of system 100.

Other modules 152 of sensor payload 140 may include other and/or additional sensors, actuators, communications modules/nodes, cooled or uncooled optical filters, and/or user interface devices used to provide additional environmental information associated with sensor payload 140, for example. In some embodiments, other modules 152 may include a humidity sensor, a wind and/or water temperature sensor, a barometer (e.g., a payload barometer), a radar system, a visible spectrum camera, an infrared camera, a GNSS, and/or other environmental sensors providing measurements and/or other sensor signals that can be displayed to a user and/or used by imaging module 142 or other devices of system 100 (e.g., controller 112) to provide operational control of platform 110 and/or system 100 or to process imagery to compensate for environmental conditions.

In general, each of the elements of system 100 may be implemented with any appropriate logic device (e.g., processing device, microcontroller, processor, application specific integrated circuit (ASIC), field programmable gate array (FPGA), memory storage device, memory reader, or other device or combinations of devices) that may be adapted to execute, store, and/or receive appropriate instructions, such as software instructions implementing a method for providing sensor data and/or imagery, for example, or for transmitting and/or receiving communications, such as sensor signals, sensor information, and/or control signals, between one or more devices of system 100.

In addition, one or more non-transitory mediums may be provided for storing machine readable instructions for loading into and execution by any logic device implemented with one or more of the devices of system 100. In these and other embodiments, the logic devices may be implemented with other components where appropriate, such as volatile memory, non-volatile memory, and/or one or more interfaces (e.g., inter-integrated circuit (I2C) interfaces, mobile industry processor interfaces (MIPI), joint test action group (JTAG) interfaces (e.g., IEEE 1149.1 standard test access port and boundary-scan architecture), and/or other interfaces, such as an interface for one or more antennas, or an interface for a particular type of sensor).

Sensor signals, control signals, and other signals may be communicated among elements of system 100 using a variety of wired and/or wireless communication techniques, including voltage signaling, Ethernet, WiFi, Bluetooth, Zigbee, Xbee, Micronet, or other medium and/or short range wired and/or wireless networking protocols and/or implementations, for example. In such embodiments, each element of system 100 may include one or more modules supporting wired, wireless, and/or a combination of wired and wireless communication techniques. In some embodiments, various elements or portions of elements of system 100 may be integrated with each other, for example, or may be integrated onto a single printed circuit board (PCB) to reduce system complexity, manufacturing costs, power requirements, coordinate frame errors, and/or timing errors between the various sensor measurements.

Each element of system 100 may include one or more batteries, capacitors, or other electrical power storage devices, for example, and may include one or more solar cell modules or other electrical power generating devices. In some embodiments, one or more of the devices may be powered by a power source for platform 110, using one or more power leads. Such power leads may also be used to support one or more communication techniques between elements of system 100.

FIG. 2 illustrates a diagram of mobile platforms (UAVs) 110A and 110B of UAS 200 including imaging systems/sensor payloads 140 and associated gimbal systems 122 in accordance with an embodiment of the disclosure. In the embodiment shown in FIG. 2, UAS 200 includes base station 130, UAV 110A with articulated imaging system/sensor payload 140 and gimbal system 122, and UAV 110B with articulated imaging system/sensor payload 140 and gimbal system 122, where base station 130 may be configured to control motion, position, and/or orientation of UAV 110A, UAV 110B, and/or sensor payloads 140.

Many UAVs are designed to fly or hover during their reconnaissance or observation missions while powered by an onboard battery that is required to supply power for propulsion, onboard sensors, and other electronics. The battery life therefore provides a maximum mission length for the UAV. Other UAVs may be configured to be powered via a microfilament deployed from a ground location during their operation thereby extending mission length while restricting the mission flight area in most cases based on the length of the filament. Embodiments described herein may include controlled operation of tethered UAVs with which power, control, and communication signals are transmitted to the UAV. The control station (e.g., base station 130) and UAV include power management systems and control circuits to control takeoff, flight operation, and landing of the UAV. One or more controllers located with the control station, on the UAV or connected by a communications network are configured to execute instructions to operate the system. In one embodiment, a UAV may draw power from remote sources (via tether), from on-board batteries, or from both, as required by operator command or by autonomous control. This ability allows, among other features, a ground or water based UAV to have a power source for safe, controlled landings upon interruption of a tethered power source.

Various embodiments of a UAS, as described herein, include a tether management system having a relatively high tether deployment and retrieval rate. A static assembly can be used on which the tether can be positioned for deployment and retrieval. A moveable actuator may contact the tether to separate the tether from the static assembly during deployment or retrieval in response to commands from a control system that responds to both manual and stored instructions to coordinate tether management with UAV flight control functions.

In some embodiments, a UAS incorporating a tethered UAV may be referred to as a Persistent Aerial Reconnaissance and Communication (PARC) System that offers extended flight time for the UAV through the use of microfilament, which may be implemented by a pair of threadlike wires that can transmit over a kilowatt of power to the UAV while also enabling transmission of bi-directional control and or sensor data, including high-definition video. A PARC system may be rapidly deployed as a low-maintenance UAV based UAS that allows cameras, radios, or other payloads to remain in operation for long durations. A PARC system may be designed to be intuitively simple to launch/land, and a small logistics footprint may make the system appropriate for austere environments. A PARC system may require minimal training for operations and maintenance. A PARC system may be designed for quick and simplified deployment to minimize operator management while maximizing capability provided in terms of communications extension, force protection, persistent stare, and tactical intelligence.

FIG. 3A illustrates a diagram of a UAS 300 including a tethered UAV 110 in accordance with an embodiment of the disclosure. In some embodiments, UAS 300 may be implemented as a PARC system. UAS 300 includes tethered UAV 110 equipped with a payload 140, a tether management system 360, and a base station 330. UAS 300 may also include a data platform adapter/media converter (DPA/MC) 334 that is coupled to an operator control unit (OCU) 332. Payload 140 may be a camera, radar, or other type of surveillance, communication, or other sensor required by a particular application of the PARC system. In general, system 300 may be an embodiment of system 100 of FIG. 1, where each of base station 330, OCU 332, DPA/MC 334, and/or tether management system 360 may be elements of base station 130 (e.g., and/or other modules 136) of system 100.

Tether management system 360 may be a ground based component that includes a spool assembly that houses a tether spool assembly, which may be a cylindrical hub that holds a pre-wound amount of micro-filament tether to be attached to UAV 110. For example, in one embodiment, the spool assembly may hold 167.6 meters (550 feet) of micro-filament tether. In one embodiment, the micro-filament tether may be Kevlar-jacketed twisted copper pair with insulation that provides both a power link and a communication link between tether management system 360 and UAV 110. Base station 330 may be connected to tether management system 360. Base station 330 may include an assembly that houses an AC power input and high voltage conversion electronics in an environmentally sealed enclosure. Base station 330 may also include a high voltage output port to supply high voltage to tether management system 360, which delivers the high voltage via the microfilament to UAV 110. A data platform adapter/media converter (DPA/MC) 334 may serve the function of connecting OCU 332 to base station 330 while also providing electrical shock hazard isolation. DPA/MC 334 may include an optical port to connect to base station 330 via a fiber optic cable and may also include an Ethernet port to connect to OCU 332. OCU 332 may be a ruggedized laptop or other computing device equipped with and able to execute an OCU application enabling control of UAV 110. Further details regarding the operation of tethered and untethered vehicles can be found in U.S. Pat. Nos. 7,510,142 and 7,631,834, the entire contents of which are incorporated herein by reference.

FIG. 3B illustrates a diagram of communication and power interconnections for UAS 300 in accordance with an embodiment of the disclosure. As shown in FIG. 3B, base station 330 may convert power (e.g., provided by source 336) to high voltage power and provide high voltage power to tether management system 360. Base station 330 may also provide a communication link over Ethernet and low voltage power to tether management system 360. Tether management system 360 may provide the high voltage power over the microfilament tether to UAV 110 for use for energy intensive operations such as radar sensing and propulsion during flight operations. As noted above, the microfilament may also provide a communication pathway used to communicate with UAV 110 by an operator of OCU 332 and/or UAS 300. DPA/MC 334 may communicate with base station 330 over an optical fiber and communicate with OCU 332 over an Ethernet connection.

For UAVs, especially quadcopters, which are not able or permitted to ascend very high, the height above ground level (AGL) is generally more important than altitude/elevation above sea level (ASL) (e.g., the absolute altitude), due to risk of collision with trees and/or buildings that project from and are therefore referenced to the local ground altitude.

A substantially real time flight altitude may be estimated based on real time measurements of atmospheric pressure using a flight barometer mounted to the UAV and Pascal's Law: ΔP=ρgΔh, where ΔP is the difference in pressure between the flight pressure at the UAV and a reference demark pressure (given in pascals in the SI system) at the ground station; p is the (average) local air density (in kilograms per cubic meter in the SI system); g is acceleration due to gravity (in meters per second squared in the SI system); and Δh is the difference in elevation between the same two positions (of the UAV and the ground station) used to determine ΔP (in meters in the SI system). However, if the reference demark pressure is assumed to be constant, such determination is subject to significant drift when the UAV is aloft for relatively long periods of time (e.g., beyond 0.5 hours or more).

For example, the take-off position (home position) may be used as the position to measure the reference demark pressure, and that reference demark pressure may be provided by either the flight barometer or the demark barometer and stored before take-off. Under such conditions, the flight altitude or height estimate is: H=(P0−P)/ρg, where H is the flight altitude estimate; P0 is the reference demark pressure; P is the ambient flight pressure measured at the UAV from the flight barometer; p (the local air density) can be set to a proper value or calculated by P/RT, where the gas constant for dry air R=287.058 J/(kg·K) and T is the ambient temperature in K; and g is set to 9.81 m/s2. An example flow diagram of a control loop 400 to determine a flight altitude estimate, where the reference demark pressure is assumed to be constant, is provided in FIG. 4.

In particular, block 402 of control loop 400 represents initiation of execution of control loop 400 (e.g., by controller 112 of UAV 110 and/or user interface 132 of base station 130 or OCU 332), which may include initializing a fight barometer mounted to UAV 110. Block 404 represents a delay of further execution until UAV 110 receives or generates a flight initiation command (e.g., to take off at or near base station 130/330). In block 406, UAV 110 receives a ground or reference flight pressure measurement P0 from the flight barometer coupled to UAV 110 after the flight initiation command is received or generated and before flight initiation commences, for example, and stores the ground or reference flight pressure measurement P0. In block 408, UAV 110 determines it has initiated flight, such as by evaluating telemetry from various sensors, for example, and proceeds to block 410.

In block 410, periodic flight pressure measurements P are made using the flight barometer based on various criteria, such as reaching a preset maximum time duration between flight pressure measurements, reaching a designated waypoint in a planned route, and/or during a relatively complex maneuver, where the flight pressure measurements may be made at approximately the maximum rate supported by the flight barometer and/or various elements of system 100. In block 412, a flight altitude estimation H is determined based on the stored ground or reference fight pressure measurement P0 and the most recent flight pressure measurement P. In some embodiments, such flight altitude estimation may be used for autopiloting UAV 110 and/or stored for later telemetry graphing or mapping, for example, and/or may be communicated to base station 130/330 as telemetry data for remote storage and/or display to an operator of system 100. In block 414, UAV 110 determines whether it has completed a flight or landed, such as by evaluating telemetry from various sensors, for example, and either continues to iteratively execute blocks 410-414 (e.g., while still in flight or executing a planned route), or proceeds to block 416, which represents ending execution of control loop 400.

Such method can work well for relatively short flights (e.g., lasting less than 0.5 or 1 hours). However, ambient pressure is always changing. For example, FIGS. 5A-B show graphs of atmospheric pressure trends in Waterloo Ontario Canada in January 2018. Looking at January 1 as an example, the atmospheric pressure rose from 99600 Pa to 100100 Pa in the first 2 hours of the day (ambient temperature was approximately 5° C.). If a UAV took off at 12:00 am, quickly ascended to 100 m, and maintained that height for 2 hours, it would drift to an actual flight altitude of 140.7 m above the ground at 2:00 am due to reference pressure change:

$\begin{matrix} {{\Delta H} = {\Delta{P/p}g}} \\ {= {{\Delta PR}{T/P}g}} \\ {= {\left( {{100100} - {99600}} \right)^{*}28{7.0}58^{*}{\left( {5 + {27{3.1}5}} \right)/\left( {100100^{*}{9.8}1} \right)}}} \\ {= {40.7{m.}}} \end{matrix}$

Embodiments described herein update the reference demark pressure using a demark barometer mounted to the base station (e.g., communicatively coupled to the base station and kept at a relatively fixed altitude). For example, the demark barometer (e.g., other modules 136) may be integrated with the base station or plugged into or electrically coupled to the base station. Reference demark pressures may be communicated to the UAV over one or more wired and/or wireless communication links established between the base station and the UAV, for example, and the UAV may be configured to determine a flight altitude estimate based on the reference demark pressures and flight pressures provided by a flight barometer (e.g., other modules 126 and/or 152) mounted to the UAV.

In various embodiments, it is not necessary to keep the location of the demark barometer constant (e.g., the same as the take-off location of the UAV), because the flight altitude estimation can compensate for a demark location change using a demark excursion pressure adjustment defined as the pressure difference between the a first demark pressure at the take-off location and a second demark pressure at a new location, where the change in location (e.g., the base station exclusion) takes place over a relatively short period of time (e.g., less than approximately 1 hour). The demark excursion pressure adjustment may be added to the subsequent series of reference demark pressures or subtracted from subsequent flight pressures, and then the flight altitude estimation may proceed as normal.

As ambient atmospheric pressure change is a relatively slow process, the update frequency of the reference demark pressure can be 1 Hz or lower. However, the validation of the measurement should be implemented as part of the flight control process, for example, so as to avoid sudden ascents/descents due to intermittently inaccurate, garbled, or wild readings or sensor failure. For example, assuming the reference demark pressure P0 is 101325 Pa, if a subsequent demark pressure measurement is out of the range 96325 Pa to 106325 Pa (P0−5000 Pa to P0+5000 Pa, where 5000 Pa is a predetermined demark pressure dynamic range threshold), that subsequent demark pressure measurement is considered invalid and omitted from the flight altitude estimation. Such dynamic range threshold may be suspended or increased while the base station location is changed, such as by user input provided to the base station.

FIG. 6 illustrates a flow chart of a control loop to determine flight altitude estimates where the reference demark pressure is not assumed to be constant. In particular, block 602 of control loop 400 represents initiation of execution of control loop 600 (e.g., by controller 112 of UAV 110 and/or user interface 132 of base station 130 or OCU 332), which may include initializing a fight barometer mounted to UAV 110 and/or a demark barometer mounted to base station 130/330. Block 604 represents a delay of further execution of control loop 600 until UAV 110 receives or generates a flight initiation command (e.g., to take off at or near base station 130/330). In block 606, UAV 110 receives a ground or reference pressure measurement P0 from the flight barometer coupled to UAV 110 after the flight initiation command is received or generated and before flight initiation commences, for example, and stores the ground or reference pressure measurement P0. At approximately the same time, base station 130/330 receives a ground or reference pressure measurement Pg0 from a demark barometer mounted to base station base station 130/330 after the flight initiation command is received or generated and before flight initiation commences, for example, and stores the ground or reference pressure measurement Pg0. In various embodiments, such ground or reference pressure measurements may be stored locally at either UAV 110 and/or base station 130/330, for example, and/or may be communicated to UAV 110 and/or base station 130/330 as telemetry data for remote storage, for example, and/or for display to an operator of system 100. In block 608, UAV 110 determines it has initiated flight, such as by evaluating telemetry from various sensors, for example, and proceeds to blocks 620 and 630.

In block 620, periodic flight pressure measurements P are made using the flight barometer based on various criteria, such as reaching a preset maximum time duration between flight pressure measurements, reaching a designated waypoint in a planned route, and/or during a relatively complex maneuver, where the flight pressure measurements may be made up to approximately the maximum rate supported by the flight barometer and/or various elements of system 100. In block 630, and substantially in parallel, with block 620, periodic demark pressure measurements Pg are made using the demark barometer based on various criteria, such as reaching a preset maximum time duration between demark pressure measurements, for example, and/or during a relatively dynamic atmospheric pressure period, where the atmospheric pressures vary relatively rapidly and the demark pressure measurements may be made up to approximately the maximum rate supported by the demark barometer and/or various elements of system 100. In some embodiments, such criteria for the demark pressure measurements may include receiving user input indicating a change in location of base station 130/330, for example, where the user indicates the start and end of such change in location so that a demark excursion pressure adjustment may be determined and/or stored based on the differential demark pressures attributed to the location change, as described herein. In various embodiments, the timing criteria of periodic flight and demark pressure measurements may be substantially synchronized in time. In block 632, measured demark pressures are checked against a demark pressure dynamic range threshold before such demark pressures are stored and/or used to determine a flight altitude estimation, as shown in block 610.

In block 610, a real-time pressure differential flight altitude estimation H is determined (e.g., by controller 112 and/or various elements of systems 100/300) based on the stored ground or reference flight pressure measurement P0, the stored ground or reference demark pressure measurement Pg0, and the most recent flight pressure measurement P and demark pressure measurement Pg. In some embodiments, such differential flight altitude estimation H may be used for autopiloting UAV 110 and/or stored for later telemetry graphing or mapping, for example, and/or may be communicated to base station 130 as telemetry data for remote storage and/or display to an operator of system 100. As discussed herein, such differential flight altitude estimation H is a substantially more reliable flight altitude estimation with respect to the actual altitude of UAV 110, particularly when flown over relatively long periods of time (e.g., over 1 hour). In various embodiments, differential flight altitude estimation H may be determined from H=(P0+(Pg−Pg0)−P)/pg. In block 614, UAV 110 determines whether it has completed a flight or landed, such as by evaluating telemetry from various sensors, for example, and either continues to iteratively execute blocks 620-632 (e.g., while still in flight or executing a planned route), or proceeds to block 614, which represents ending execution of control loop 600.

FIG. 7 illustrates a flow diagram 700 of various operations to provide flight altitude estimates using UASs 100 and/or 300 in accordance with an embodiment of the disclosure. In some embodiments, the operations of FIG. 7 may be implemented as software instructions executed by one or more logic devices or controllers associated with corresponding electronic devices, sensors, control loops, and/or structures depicted in FIGS. 1-6. More generally, the operations of FIG. 7 may be implemented with any combination of software instructions, mechanical elements, and/or electronic hardware (e.g., inductors, capacitors, amplifiers, actuators, or other analog and/or digital components). It should also be appreciated that any step, sub-step, sub-process, or block of process 700 may be performed in an order or arrangement different from the embodiment illustrated by FIG. 7. For example, in other embodiments, one or more blocks may be omitted from or added to the process. Furthermore, block inputs, block outputs, various sensor signals, sensor information, calibration parameters, and/or other operational parameters may be stored to one or more memories prior to moving to a following portion of a corresponding process. Although process 700 is described with reference to systems described in FIGS. 1-6, process 700 may be performed by other systems different from those systems and including a different selection of electronic devices, sensors, assemblies, mechanisms, platforms, and/or platform attributes.

At block 702, flight pressure data is received. For example, controller 112, communication module 120, user interface 132, and/or communication module 132 may be configured to receive flight pressure data generated by a flight barometer mounted to UAV 110. In various embodiments, such flight pressure data may be received as UAV 110 maneuvers within a survey area, either while tethered or under free flight conditions. At block 704, demark pressure data is received. For example, controller 112, communication module 120, user interface 132, and/or communication module 132 may be configured to receive demark pressure data generated by a demark barometer mounted to base station 130. In various embodiments, such demark pressure data may be received as UAV 110 maneuvers within a survey area, for example, or as base station is moved between locations while remaining able to communicate with UAV 110. In block 706, a differential flight altitude estimation is determined. For example, controller 112, communication module 120, user interface 132, and/or communication module 132 may be configured to determine the differential flight altitude estimation based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station, as described herein.

In various embodiments, a time series of such differential flight altitude estimations may be determined, such as corresponding to one or more positions of UAV 110 within a survey area, for example, and an elevation map may be generated and/or displayed to an operator of systems 100/300, based on the time series of differential flight altitude estimations. In some embodiments, such differential flight altitude estimations may be used to autopilot UAV 110 according to a designated surveillance route and/or tether extent, for example.

By providing such systems and techniques for flight altitude estimation, embodiments of the present disclosure substantially improve the operational flexibility and reliability of unmanned sensor platforms. Moreover, such systems and techniques may be used to increase the operational safety of unmanned mobile sensor platforms above that achievable by conventional systems. As such, embodiments provide mobile sensor platforms systems with significantly increased survey convenience and performance.

Where applicable, various embodiments provided by the present disclosure can be implemented using hardware, software, or combinations of hardware and software. Also, where applicable, the various hardware components and/or software components set forth herein can be combined into composite components comprising software, hardware, and/or both without departing from the spirit of the present disclosure. Where applicable, the various hardware components and/or software components set forth herein can be separated into sub-components comprising software, hardware, or both without departing from the spirit of the present disclosure. In addition, where applicable, it is contemplated that software components can be implemented as hardware components, and vice-versa.

Software in accordance with the present disclosure, such as non-transitory instructions, program code, and/or data, can be stored on one or more non-transitory machine readable mediums. It is also contemplated that software identified herein can be implemented using one or more general purpose or specific purpose computers and/or computer systems, networked and/or otherwise. Where applicable, the ordering of various steps described herein can be changed, combined into composite steps, and/or separated into sub-steps to provide features described herein.

Embodiments described above illustrate but do not limit the invention. It should also be understood that numerous modifications and variations are possible in accordance with the principles of the present invention. Accordingly, the scope of the invention is defined only by the following claims. 

1. A system comprising: a logic device configured to communicate with a communication module and a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the communication module is configured to establish a communication link with a base station associated with the UAV, the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area, and the logic device is configured to: receive flight pressure data from the flight barometer corresponding to one or more positions of the UAV within the survey area; receive demark pressure data from a demark barometer coupled to the base station; and determine a differential flight altitude estimation based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station.
 2. The system of claim 1, wherein the logic device is configured to: determine a time series of differential flight altitude estimations based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station; and generate an elevation map corresponding to the one or more positions of the UAV within the survey area, wherein the elevation map is based, at least in part, on the determined time series of differential flight altitude estimations.
 3. The system of claim 1, wherein the logic device is configured to: autopilot the UAV according to a designated surveillance route based, at least in part, on the determined differential flight altitude estimation.
 4. The system of claim 1, wherein the logic device is configured to: determine a demark excursion pressure adjustment based, at least in part, on first and second demark pressures associated with respective first and second locations of the base station; and determine the differential flight altitude estimation based, at least in part, on the determined demark excursion pressure adjustment.
 5. The system of claim 1, wherein: the logic device is coupled to the UAV; and the reference demark pressure is received from the base station over the communication link and stored at the UAV.
 6. The system of claim 1, wherein: the logic device is coupled to the base station; and the reference flight pressure is received from the UAV over the communication link and stored at the base station.
 7. The system of claim 1, further comprising: the UAV comprising the communication module and the flight barometer; and wherein the communication link is via a tether coupled to the UAV.
 8. The system of claim 7, further comprising: the base station; and wherein the tether is coupled between the UAV and the base station.
 9. The system of claim 8, wherein: the base station further comprises the demark barometer; and the UAV comprises a fixed wing or a copter type of aircraft.
 10. A method of using the system of claim 1, the method comprising: receiving the flight pressure data from the flight barometer coupled to the UAV, wherein the flight barometer provides flight pressures associated with the UAV as it maneuvers within the survey area and the flight pressure data corresponds to one or more positions of the UAV within the survey area; receiving the demark pressure data from the demark barometer coupled to the base station; and determining the differential flight altitude estimation based, at least in part, on the received flight pressure data and the demark pressure data, the reference flight pressure corresponding to the flight initiation location of the UAV, and the reference demark pressure corresponding to the flight initiation location of the base station.
 11. A method comprising: receiving flight pressure data from a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area and the flight pressure data corresponds to one or more positions of the UAV within the survey area; receiving demark pressure data from a demark barometer coupled to a base station; and determining a differential flight altitude estimation based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station.
 12. The method of claim 11, further comprising: determining a time series of differential flight altitude estimations based, at least in part, on the received flight pressure data and demark pressure data, a reference flight pressure corresponding to a flight initiation location of the UAV, and a reference demark pressure corresponding to a flight initiation location of the base station; and generating an elevation map corresponding to the one or more positions of the UAV within the survey area, wherein the elevation map is based, at least in part, on the determined time series of differential flight altitude estimations.
 13. The method of claim 11, further comprising: autopiloting the UAV according to a designated surveillance route based, at least in part, on the determined differential flight altitude estimation.
 14. The method of claim 11, further comprising: determining a demark excursion pressure adjustment based, at least in part, on first and second demark pressures associated with respective first and second locations of the base station; and determining the differential flight altitude estimation based, at least in part, on the determined demark excursion pressure adjustment.
 15. The method of claim 11, wherein: the reference demark pressure is received from the base station over a communication link and stored at the UAV.
 16. The method of claim 11, wherein: the reference flight pressure is received from the UAV over a communication link and stored at the base station.
 17. The method of claim 11, wherein communication between the base station and the UAV is via a tether coupled between the UAV and the base station.
 18. A system for performing the method of claim 11, the system comprising: a logic device configured to perform the determining of the differential flight altitude estimation; the base station; and the UAV comprising the flight barometer.
 19. The system of claim 18, wherein: the base station comprises the demark barometer; and the UAV comprises a fixed wing or a copter type of aircraft.
 20. The system of claim 18, further comprising: a tether coupled between the UAV and the base station and configured to provide power to the UAV and form a communication link between the UAV and the base station. 